Determine the pressure and temperature at each point in the

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Consider an air-standard gas Turbine cycle with a regenerator heat exchanger. The operating compression ratio oand a maximum combustion temperature of the system are 12 and 1200 C respectively. The state of the air at intake is given as pressure of 0.1 MPa and temperature of 20 C. The Assume efficiencies of turbine, compressor and regenerators as 90%. Determine the pressure and temperature at each point in the cycle and the thermal efficiency. Give a summary table for the ratings for each component of the gas turbine system.

Reference no: EM13637894

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